Gas turbine engines

Claim 2

A gas turbine engine fuel supply system comprising: upper and lower, arcuately shaped fuel manifolds having, together, an essentially circular configuration; a circular array of equiangularly spaced fuel injectors spaced concentrically within the circle formed by said manifolds; fuel lines connecting those fuel injectors girdled by each of the manifolds to that manifold at generally equidistantly spaced locations therealong; means for supplying fuel to the upper manifold at the opposite ends thereof; a fuel supply line connected between said fuel supplying means and said lower manifold approximately mid way between the ends of the latter; and means in said fuel supply line for creating a pressure drop that is effective to cause said fuel to be distributed at rates approaching equal through the upper and lower fuel manifolds.

Claim 3

A gas turbine engine fuel supply system as defined in claim 1 wherein the means for creating said pressure drop is a check valve oriented to allow fuel to flow from said fuel supplying means through said fuel supply line to said lower manifold.

Claim 4

A gas turbine engine fuel supply system as defined in either of the preceding claims 1 or 2 which includes means for draining fuel from said lower manifold coincidentally with the shutdown of the engine with which the fuel supply system is associated, said means comprising a fuel return line connected between said fuel supplying means and said lower manifold adjacent said fuel supply line and a check valve in said fuel return line which is oriented to allow fuel to flow from said lower manifold into said fuel supplying means when the pressure in the latter falls below the pressure in the lower manifold.

Claim 5

A gas turbine engine fuel supply system as defined in either of the preceding claims 1 or 2 wherein said fuel supplying means comprises a first, generally semicircular fuel line means surrounding the lower manifold and connected at its opposite ends to the ends of the upper manifold and a second fuel line communicating with the first fuel line approximately mid way between the ends of the latter.

Claim 6

A gas turbine engine fuel supply system as defined in either of the preceding claims 1 or 2 wherein said fuel injectors are of the air blast type.

Claim 7

A gas turbine engine comprising a combustor, a circular array of equiangularly spaced fuel injectors for introducing a liquid fuel into the combustor in atomized form, and means for effecting a flow of fuel to, and through, said injectors, said last-mentioned means comprising: upper and lower, arcuately shaped fuel manifolds having, together, an essentially circular configuration; fuel lines connecting those fuel injectors girdled by each of the manifolds to that manifold at generally equidistantly spaced locations therealong; means for supplying fuel to the upper manifold at the opposite ends thereof; a fuel supply line connected between said fuel supplying means and said lower manifold approximately mid way between the ends of the latter; and means in said fuel supply line for creating a pressure drop that is effective to cause said fuel to be distributed at rates approaching equal through the upper and lower fuel manifolds.

Claim 8

A gas turbine engine comprising a combustor, a circular array of equiangularly spaced fuel injectors for introducing a liquid fuel into the combustor in atomized form, and means for effecting a flow of fuel to, and through, said injectors, said last-mentioned means comprising: upper and lower, arcuately shaped fuel manifolds having, together, an essentially circular configuration; fuel lines connecting those fuel injectors girdled by each of the manifolds to that manifold at generally equidistantly spaced locations therealong; means for supplying fuel to the upper manifold at the opposite ends thereof; a fuel supply line connected between said fuel supplying means and said lower manifold approximately mid way between the ends of the latter; and means in said fuel supply line for creating a pressure drop that is effective to cause said fuel to be distributed at rates approaching equal through the upper and lower fuel manifolds.

Claim 9

A gas turbine engine as defined in claim 6 wherein the means for creating said pressure drop is a check valve oriented to allow fuel to flow from said fuel supplying means through said fuel supply line to said lower manifold.

Claim 10

A gas turbine engine as defined in either of the preceding claims 6 or 7 which includes means for draining fuel from said lower manifold coincidentally with the shutdown of the engine with which the fuel supply system is associated, said means comprising a fuel return line connected between said fuel supplying means and said lower manifold adjacent said fuel supply line and a check valve in said fuel return line which is oriented to allow fuel to flow from said lower manifold into said fuel supplying means when the pressure in the latter falls below the pressure in the lower manifold.

Claim 11

A gas turbine engine fuel supply system as defined in either of the preceding claims 6 or 7 wherein said fuel supplying means comprises a first, generally semicircular fuel line means surrounding the lower manifold and connected at its opposite ends to the ends of the upper manifold and a second fuel line communicating with the first fuel line approximately mid way between the ends of the latter.

Claim 12

A gas turbine engine fuel supply system as defined in either of the preceding claims 6 or 7 wherein said fuel injectors are of the air blast type.